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Characterizing Flow Effects of Ported Shroud Casing Treatment on Centrifugal Compressor Performance

机译:表征带口罩壳处理对离心压缩机性能的流动影响

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摘要

This paper presents an investigation of the effects of ported shroud (PS) self-recirculating casing treatment used in turbocharger centrifugal compressors for increasing the operable range. The investigation consists of computing three-dimensional flow in a representative centrifugal compressor with and without PS at various levels of approximations in flow physics and geometrical configuration; this provides an enabler for establishing the causal link between PS flow effects and compressor performance changes. It is shown that the main flow path perceives the PS flow as a combination of flow actuations that include injection and removal of mass flow and injection of axial momentum and tangential momentum. A computational model in which the presence of the PS is replaced by imposed boundary conditions (BCs) that reflect the individual flow actuations has thus been formulated and implemented. The removal of a fraction of the inducer mass flow has been determined to be the dominant flow actuation in setting the performance of PS compressors. Mass flow removal reduces the flow blockage associated with the impeller tip leakage flow and increases the diffusion in the main flow path. Adding swirl to the injected flow in the direction opposite to the wheel rotation results in an increase of the stagnation pressure ratio and a decrease of the efficiency. The loss generation in the flow path has been defined to rationalize efficiency changes associated with PS compressor operation.
机译:本文对涡轮增压器离心式压缩机中使用的带孔罩(PS)自循环套管处理的效果进行了研究,以扩大可使用范围。研究包括在具有和不具有PS的有代表性的离心式压缩机中,在流体物理和几何构型的各种近似水平下,计算三维流动;这为建立PS流量影响与压缩机性能变化之间的因果关系提供了推动力。结果表明,主流动路径将PS流感知为流驱动的组合,包括注入和去除质量流以及注入轴向动量和切向动量。因此,已经制定并实现了一种计算模型,在该模型中,PS的存在被反映单个流量驱动的强加边界条件(BCs)代替。在设置PS压缩机的性能时,已确定去除一部分进气质量流量是主要的流量驱动。去除质量流可减少与叶轮尖端泄漏流相关的流阻,并增加主流路中的扩散。在与车轮旋转相反的方向上向喷射流中增加涡流会导致停滞压力比增加,效率降低。已经定义了流路中的损失产生,以合理化与PS压缩机运行相关的效率变化。

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  • 来源
    《Journal of turbomachinery》 |2017年第8期|081005.1-081005.12|共12页
  • 作者单位

    Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139;

    Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139;

    Honeywell Turbo Technologies, Torrance, CA 90504;

    Honeywell Turbo Technologies, Torrance, CA 90504;

    Honeywell Turbo Technologies, Torrance, CA 90504;

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